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In a single multi-stage propellant rocket engine, standardizing and automating the loading of the propellant would provide advantages. For example, loading the propellant into the engine may be automated, thereby avoiding the need for personnel to engage in the process, as well as the time-consuming process of loading propellant into the engine. A significant increase in efficiency through a reduction of inefficiencies and costs associated with engine loading may be obtained when the aforementioned problems are addressed.
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